Gas flow separator with a thermal bridge de-icer

Abstract

The invention relates to a gas flow separator dividing the flow into a primary and a secondary stream, especially for a dual rotor axial turbomachine. The separator comprises a splitter nose of the turbomachine and includes a generally wedge-shaped leading edge in the gas flow to be split. The flow separator also comprises a metal blade having a longitudinal section in the form of an “S” and located in the nose in contact with the back of the leading edge and extending from the leading edge to a rear end of the separator at some distance from the leading edge, so as to be in contact with a heat source, such as a heat exchanger, located at some distance from the leading edge.

What is claimed is: 
     
       1. A gas flow separator for splitting a gas flow into a first flow and a second flow, said separator comprising:
 a separator leading edge; and 
 a leading edge de-icing device comprising at least a metal blade in thermal contact with the leading edge and extending from the leading edge to a rear end of the separator at some distance from leading edge where the metal blade is in thermal contact with a heat source located at some distance from the leading edge. 
 
     
     
       2. The separator in accordance with  claim 1 , wherein the contact between the metal blade and the leading edge is provided by insertion of the blade into a slot disposed within the separator and close to the leading edge. 
     
     
       3. The separator in accordance with  claim 1 , wherein the separator comprises a guide wall of the first flow and a guide wall of the second flow, and the metal blade is in thermal contact with the guide wall of the first flow and the guide wall of the second flow. 
     
     
       4. The separator in accordance with  claim 3 , wherein the metal blade is held in place by attaching a rear end of the metal blade to the guide wall of the second flow. 
     
     
       5. The separator in accordance with  claim 3 , wherein the metal blade extends mainly along the guide wall of the second flow, having an insulating material placed between the guide wall of the second flow and the metal blade. 
     
     
       6. The separator in accordance with  claim 5 , wherein the metal blade is made of a single piece with the leading edge and the guide wall of the second flow is fixed to the blade by the insulating material. 
     
     
       7. The separator in accordance with  claim 1 , wherein the metal blade has a longitudinal cross-section generally in the shape of an “S”, having a substantially straight front end and a substantially straight rear end. 
     
     
       8. The separator in accordance with  claim 1  wherein the separator comprises a splitter nose for dividing a gas flow in a dual rotor axial turbomachine, the first flow being the primary flow and the second flow being the secondary flow of the dual rotor turbomachine. 
     
     
       9. The separator in accordance with  claim 8 , wherein the splitter nose comprises a guide wall of the secondary flow, and the metal blade is in contact with a rear end of the guide wall of the secondary flow. 
     
     
       10. The separator in accordance with  claim 9  further comprising a surface heat exchanger surface in the extension of the guide wall of the secondary flow and the metal blade is in thermal contact with the heat exchanger. 
     
     
       11. The separator in accordance with  claim 10  wherein the rear end of the guide wall for secondary flow, a front end of the heat exchanger, and a rear end of the blade form a stacked assembly. 
     
     
       12. The separator in accordance with  claim 11 , wherein the metal blade comprises at least one female threaded member intended to mate with a bolt passing through the stacked assembly. 
     
     
       13. The separator in accordance with  claim 12  wherein the metal blade has an approximately circular cross-section. 
     
     
       14. The separator in accordance with  claim 12  wherein the de-icing device comprises a plurality of blades each having an approximately arcuate cross-section. 
     
     
       15. The compressor in accordance with  claim 14 , wherein the metal blade is in thermal contact with a heat source located at some distance from the leading edge. 
     
     
       16. A dual rotor axial turbomachine compressor comprising a separator for separating an air flow into a primary and a secondary stream, the separator comprising:
 a separator leading edge; and 
 a leading edge de-icing device comprising at least a metal blade in thermal contact with the leading edge and extending from the leading edge to a rear end of the separator at some distance from leading edge where the metal blade is in thermal contact with a heat source located at some distance from the leading edge.